چكيده به لاتين
Among the various types of satellite formations, the application of leader-follower is the most popular because of some of the features, including simplicity in analysis and implementation. One of the important goals in satellite formation is to control the relative position of the satellites (formation keeping). On the other hand, it is sometimes necessary during the mission to reconfiguration and create a new configuration, which is another goal. But various kinds of disturbances and indeterminacy, also variations in some of the parameters, including mass (due fuel consumption), are challenges that exist in practice. In this thesis, a leader-follower formation consisting of three satellites is considered, and with considering an uncertainty in the mass of satellites as well as an error in estimating the relative position of satellites, an adaptive proportional-integral sliding mode controller for all three stages of formation make-up, formation keeping and change in configuration (reconfiguration) has been designed and compared with the two method; adaptive sliding mode and linear quadratic regulator. Since there is an error in estimation position of satellites, this controller is has been designed to tolerate this error and there is no chattering phenomenon. The proposed controller also reduces fuel consumption compared to the other two method.
Keywords: Satellite, Leader/follower, disturbances, uncertainties, adaptive PI sliding mode.
